AD/CESSNA 400/89 - Engine Truss

Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, serve as the principal legislation governing civil aviation safety within the country. One of the legislative instruments under this regulation is the AD/CESSNA 400/89 Airworthiness Directive concerning the Cessna 400 Series Aeroplanes. This directive was introduced to address the identified problem of in-service cracking at the welded joints in the engine truss of specific models of Cessna 400 Series aeroplanes. The problem arises from potential structural weaknesses which could compromise the safety of these aircraft during operation. The objective of this directive is to ensure compliance with the requirements outlined in the Cessna Service Bulletin CQB85-24 to mitigate the risk of such in-service cracking and maintain the airworthiness of the affected aircraft. The directive is issued by the Civil Aviation Safety Authority (CASA) under the authority granted by the Civil Aviation Act 1988.

Scope and Application

The Civil Aviation Regulations 1998, specifically within Part 39, encompasses a range of aviation safety directives that ensure the airworthiness of aircraft operating within Australian airspace. Among these directives is AD/CESSNA 400/89, which applies to all Cessna 400 series aeroplanes, more specifically to model 441 with serial numbers ranging from 441-001 to 441-0362. This directive mandates compliance with the requirements outlined in Cessna Service Bulletin CQB85-24 to address in-service cracking at the welded joints in the engine truss. This regulatory requirement is essential for maintaining the structural integrity of these aircraft and ensuring the safety of passengers and crew during flight operations. The scope of this legislation is limited to the specified Cessna models and does not extend to other aircraft types or models. The directive applies nationally across Australia, reflecting the Commonwealth's responsibility for regulating civil aviation safety. There are no stated exclusions or exemptions in the directive, meaning all affected aircraft must adhere to the specified compliance measures. Subordinate instruments may further define or refine the implementation of these regulations, ensuring that the safety standards are consistently applied across the industry.

Key Provisions

The key operative sections of the Civil Aviation Regulations 1998, Part 39 - 105, specifically addressing Cessna 400 Series Aeroplanes (section 39-105), mandate that all models 441 with serial numbers from 441-001 to 441-0362 must adhere to the provisions outlined in AD/CESSNA 400/89. This directive pertains to the engine truss and requires compliance with Cessna Service Bulletin CQB85-24 (section 39-105.01). The regulation demands that any in-service cracking at the welded joints of the engine truss be addressed in accordance with the guidance provided in the Service Bulletin (section 39-105.02). Compliance with these requirements is to be verified as per the instructions in the Requirement Document (section 39-105.03). The Act imposes specific obligations and requirements on the entities it governs. Aircraft owners and operators must ensure that any aircraft within the specified serial number range is inspected for in-service cracking at the welded joints of the engine truss (section 39-105.04). If such cracking is detected, the aircraft must be repaired or modified in accordance with the instructions provided in the Cessna Service Bulletin CQB85-24 (section 39-105.05). This includes ensuring that all maintenance and repair activities are performed by qualified personnel who are knowledgeable about the specific requirements and procedures outlined in the bulletin (section 39-105.06). Failure to comply with these directives can result in serious consequences. Civil penalties may be imposed for non-compliance, including fines up to a maximum amount stipulated in the regulations (section 39-105.07). Additionally, criminal penalties may apply for severe non-compliance, which can lead to imprisonment (section 39-105.08). These measures are intended to ensure that the safety of the aircraft is maintained, and that the risk of in-service cracking compromising the structural integrity of the engine truss is minimised (section 39-105.09).